The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source.

A liquid discharge cartridge manufacturing method includes a first step of individually shaping a first shaped member and a second shaped member that form a housing of a liquid discharge cartridge, and a second step of joining the first shaped member and the second shaped member to be bonded to each other with molten resin. The first step includes shaping a wall section in the first shaped member, the wall section forming a recess for accommodating the molten resin, and shaping a projection in the second shaped member, the projection extending such that the projection is located at the outer side of the wall section and adjacent to the wall section, with a predetermined gap being formed between the projection and the wall section, when the first and second shaped members are joined.

A nozzle arrangement is disclosed herein for use with a supersonic jet engine that is configured to produce a plume of exhaust gases. The nozzle arrangement includes, but is not limited to, a nozzle having a trailing edge and a plug body partially positioned within the nozzle. The plug body has an expansion surface and a compression surface downstream of the expansion surface. A protruding portion of the plug body extends downstream of the trailing edge for a length greater than a conventional plug body length. The plug body is configured to shape the exhaust gases to flow substantially parallel to a free stream of air flowing off of the trailing edge of the nozzle and to cause the plume of exhaust gases to isentropically turn the free stream of air to move in a direction parallel to a longitudinal axis of the plug body.

Methods for manufacturing a turbine nozzle are provided. A plurality of nozzle segments is formed. Each nozzle segment comprises an endwall ring portion with at least one vane. The plurality of nozzle segments are connected to an annular endwall forming a segmented annular endwall concentric to the annular endwall with the at least one vane of each nozzle segment extending between the segmented annular endwall and the annular endwall.

The present invention concerning of a device for mounting or dismantling, replacement and maintenance of a can-combustor of a gas turbine engine including an assembly tool or assembly tool with additional frame having at least one lifting beam, at least one linear driver, wheels, at least one eccentric rolling hook for fixation of the gas turbine housing, optionally spacers for building the interface to the can-combustor, adapters, lifting points for the main crane. The eccentric rolling hook is connected to the gas turbine housing by giving in axial or quasi-axial direction a force for mounting or dismantling the can-combustor from the gas turbine housing.

To provide a treatment device equipped with a catalyst-supporting honeycomb structure, the device being for use in, for example, an exhaust gas purification treatment, hydrogen production by ammonia decomposition or the like, and a method for producing the same. The catalyst-supporting honeycomb structure is produced by forming the inorganic binder-containing functional catalyst-supporting corrugated glass paper without removing an organic binder originally contained in the glass paper and by using the corrugated glass paper in combination with the inorganic binder-containing functional catalyst-supporting flat glass paper. In the treatment device equipped with a catalyst-supporting honeycomb structure, a corrugated glass paper having an inorganic binder-containing functional catalyst supported thereon and a flat glass paper having the same inorganic binder-containing functional catalyst supported thereon are alternately stacked to form the catalyst-supporting honeycomb structure, and this catalyst-supporting honeycomb structure is packed in a casing.

An alignment tool for use in a gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a clamp portion, a component engagement portion and an arm portion that extends between the clamp portion and the component engagement portion. The clamp portion establishes a fixed datum surface for positioning a component within the gas turbine engine.

The invention relates to a method for revamping a conventional refinery of mineral oils into a biorefinery, characterized by a production scheme which allows the treatment of raw materials of a biological origin (vegetable oils, animal fats, exhausted cooking oils) for the production of biofuels, prevalently high-quality biodiesel. This method allows the re-use of existing plants, allowing, in particular, the revamping of a refinery containing a system comprising two hydrodesulfurization units, U1 and U2, into a biorefinery containing a production unit of hydrocarbon fractions from mixtures of a biological origin containing fatty acid esters by means of their hydrodeoxygenation and isomerization, wherein each of the hydrodesulfurization units U1 and U2 comprises: a hydrodesulfurization reactor, (A1) for the unit U1 and (A2) for the unit U2, wherein said reactor contains a hydrodesulfurization catalyst; one or more heat exchangers between the feedstock and effluent of the reactor; a heating system of the feedstock upstream of the reactor; an acid gas treatment unit downstream of the reactor, containing an absorbent (B) for H.sub.2S, said unit being called T1 in the unit U1 and T2 in the unit U2, and wherein said method comprises: installing a line L between the units U1 and U2 which connects them in series; installing a recycling line of the product for the unit U1 and possibly for the unit U2, substituting the hydrodesulfurization catalyst in the reactor A1 with a hydrodeoxygenation catalyst; substituting the hydrodesulfurization catalyst in the reactor A2 with an isomerization catalyst; installing a by-pass line of the acid gas treatment unit T2 of the unit U2; substituting the absorbent (B) in the acid gas treatment unit T1 with a specific absorbent for CO.sub.2 and H.sub.2S. The operative configuration obtained with the method, object of the present invention, also leads to a substantial reduction in emissions of pollutants into the atmosphere, with respect to the original operative mode. The invention also relates to the transformation unit of mixtures of a biological origin obtained with said conversion method and particularly hydrodeoxygenation and isomerization processes.

An antivortex device for use in suppressing formation of a vortex created by fluid flowing through multiple outlet ports defined in a sump is provided. The antivortex device includes a plurality of center plates extending through a central axis of the sump, an extension plate substantially aligned with one of the plurality of center plates and extending substantially radially outward from the central axis, and a top plate coupled to the plurality of center plates.

The present invention relates to improved rocket engine systems. In one embodiment, an improved rocket engine system includes a propellant source, at least one power source, at least one power source motor, a rocket engine, and at least one pump. The improved rocket engine system may further include at least one of the following: at least one controller, at least one propellant valve, and a propellant pressurizing source.